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RU2003134537A - TURBIN SHOVEL WITH SEALING ELEMENT - Google Patents

TURBIN SHOVEL WITH SEALING ELEMENT Download PDF

Info

Publication number
RU2003134537A
RU2003134537A RU2003134537/06A RU2003134537A RU2003134537A RU 2003134537 A RU2003134537 A RU 2003134537A RU 2003134537/06 A RU2003134537/06 A RU 2003134537/06A RU 2003134537 A RU2003134537 A RU 2003134537A RU 2003134537 A RU2003134537 A RU 2003134537A
Authority
RU
Russia
Prior art keywords
extremity
blade according
sealing element
axis
blade
Prior art date
Application number
RU2003134537/06A
Other languages
Russian (ru)
Other versions
RU2296226C2 (en
Inventor
Шанталь ЖИОТ (FR)
Шанталь ЖИОТ
Жан-Люк СУПИЗОН (FR)
Жан-Люк СУПИЗОН
Original Assignee
Снекма Моторс (Fr)
Снекма Моторс
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Снекма Моторс (Fr), Снекма Моторс filed Critical Снекма Моторс (Fr)
Publication of RU2003134537A publication Critical patent/RU2003134537A/en
Application granted granted Critical
Publication of RU2296226C2 publication Critical patent/RU2296226C2/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Claims (9)

1. Лопатка (2) ротора турбины, содержащая внутреннюю поверхность (8) и внешнюю поверхность (10), расположенные по разные стороны оси (XX′) лопатки, причем лопатка (2) содержит также наконечник (6), расположенный на ее вершине, и, по меньшей мере, один уплотнительный элемент (12, 14), установленный на указанном наконечнике, причем указанный уплотнительный элемент (12, 14) расположен перпендикулярно внутренней поверхности (8) и внешней поверхности (10) и содержит первую оконечность (16, 18) со стороны внешней поверхности (10) и вторую оконечность (20, 22) со стороны внутренней поверхности (8), причем указанная первая оконечность (16, 18) имеет большую высоту, чем указанная вторая оконечность (20, 22), причем указанный уплотнительный элемент (12, 14) содержит наружную контактную поверхность (26) уплотнительного элемента, расположенную между указанными первой (16, 18) и (20, 22) второй оконечностями, отличающаяся тем, что указанная наружная контактная поверхность (26) уплотнительного элемента выполнена в виде выпуклой поверхности, проходящей от первой оконечности до второй оконечности.1. The blade (2) of the turbine rotor containing the inner surface (8) and the outer surface (10) located on opposite sides of the axis (XX ′) of the blade, and the blade (2) also contains a tip (6) located on its top, and at least one sealing element (12, 14) mounted on said tip, wherein said sealing element (12, 14) is perpendicular to the inner surface (8) and the outer surface (10) and comprises a first end (16, 18 ) from the side of the outer surface (10) and the second tip (20, 22) from the side a morning surface (8), said first extremity (16, 18) having a greater height than said second extremity (20, 22), wherein said sealing element (12, 14) comprises an outer contact surface (26) of the sealing element located between said first (16, 18) and (20, 22) second extremities, characterized in that said outer contact surface (26) of the sealing element is made in the form of a convex surface extending from the first extremity to the second extremity. 2. Лопатка по п.1, отличающаяся тем, что указанная выпуклая поверхность имеет поперечное сечение круглой формы с медианной осью (хх′), центром (О) и радиусом (R).2. The blade according to claim 1, characterized in that said convex surface has a circular cross-section with a median axis (xx ′), center (O) and radius (R). 3. Лопатка по п.2, отличающаяся тем, что указанная медианная ось (хх′) отклонена на угол (α) от оси (XX′) лопатки, причем указанный угол (α) отсчитывается от внутренней поверхности (8) к внешней поверхности (10), а центр (О) смещен от оси (XX′) лопатки на расстояние (L), измеренное в направлении, перпендикулярном оси (XX′) лопатки.3. The blade according to claim 2, characterized in that said median axis (xx ′) is deflected by an angle (α) from the axis (XX ′) of the scapula, said angle (α) being counted from the inner surface (8) to the outer surface ( 10), and the center (O) is offset from the axis (XX ′) of the scapula by a distance (L), measured in the direction perpendicular to the axis (XX ′) of the scapula. 4. Лопатка по п.3, отличающаяся тем, что расстояние (L), по меньшей мере, равно полушагу, соответствующему половине расстояния между указанной первой оконечностью (16, 18) и указанной второй оконечностью (20, 22).4. The blade according to claim 3, characterized in that the distance (L) is at least equal to a half-step corresponding to half the distance between said first extremity (16, 18) and said second extremity (20, 22). 5. Лопатка по любому из пп.1-4, отличающаяся тем, что разница высот (d) между указанной первой оконечностью (16, 18) и указанной второй оконечностью (20, 22) составляет не менее 0,2 мм.5. The blade according to any one of claims 1 to 4, characterized in that the height difference (d) between the specified first extremity (16, 18) and the specified second extremity (20, 22) is at least 0.2 mm. 6. Лопатка по любому из пп.1-3, отличающаяся тем, что она содержит два уплотнительных элемента (12, 14).6. The blade according to any one of claims 1 to 3, characterized in that it contains two sealing elements (12, 14). 7. Лопатка по п.6, отличающаяся тем, что два уплотнительных элемента (12, 14), по существу, параллельны.7. The blade according to claim 6, characterized in that the two sealing elements (12, 14) are essentially parallel. 8. Лопатка по п.5, отличающаяся тем, что она содержит два уплотнительных элемента (12, 14).8. The blade according to claim 5, characterized in that it contains two sealing elements (12, 14). 9. Лопатка по п.8, отличающаяся тем, что два уплотнительных элемента (12, 14), по существу, параллельны.9. The blade according to claim 8, characterized in that the two sealing elements (12, 14) are essentially parallel.
RU2003134537/06A 2001-05-31 2002-05-30 Turbine blade with sealing element RU2296226C2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR01/07122 2001-05-31
FR0107122A FR2825411B1 (en) 2001-05-31 2001-05-31 TURBINE DAWN WITH SEALING LECHETTE

Publications (2)

Publication Number Publication Date
RU2003134537A true RU2003134537A (en) 2005-05-10
RU2296226C2 RU2296226C2 (en) 2007-03-27

Family

ID=8863806

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2003134537/06A RU2296226C2 (en) 2001-05-31 2002-05-30 Turbine blade with sealing element

Country Status (9)

Country Link
US (1) US6939104B2 (en)
EP (1) EP1262633B1 (en)
JP (1) JP4074244B2 (en)
CA (1) CA2448802C (en)
DE (1) DE60203214T2 (en)
ES (1) ES2240670T3 (en)
FR (1) FR2825411B1 (en)
RU (1) RU2296226C2 (en)
WO (1) WO2002097241A1 (en)

Cited By (1)

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RU2415003C2 (en) * 2005-11-15 2011-03-27 Снекма Method of producing rib on vane free end, vane produced by said method and gas turbine engine equipped with said vane

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DE102004025321A1 (en) * 2004-05-19 2005-12-08 Alstom Technology Ltd Turbomachine blade
US7549841B1 (en) 2005-09-03 2009-06-23 Florida Turbine Technologies, Inc. Pressure balanced centrifugal tip seal
US20090097979A1 (en) * 2007-07-31 2009-04-16 Omer Duane Erdmann Rotor blade
FR2923524B1 (en) * 2007-11-12 2013-12-06 Snecma MOLDED METALLIC BLADE AND METHOD OF FABRICATING THE BLADE
DE102008061800A1 (en) * 2008-12-11 2010-06-17 Rolls-Royce Deutschland Ltd & Co Kg Segmented sealing lips for labyrinth seals
FR2950104B1 (en) * 2009-09-11 2011-12-09 Snecma TURBOMACHINE WHEEL
US8613596B2 (en) * 2009-12-28 2013-12-24 Rolls-Royce Corporation Vane assembly having a vane end seal
US9151166B2 (en) 2010-06-07 2015-10-06 Rolls-Royce North American Technologies, Inc. Composite gas turbine engine component
EP2412927A1 (en) * 2010-07-29 2012-02-01 Alstom Technology Ltd Turbine blade
RU2010150602A (en) * 2010-12-09 2012-06-20 Альстом Текнолоджи Лтд (Ch) ROTOR BLADE BANDAGE
ES2773743T3 (en) * 2011-12-13 2020-07-14 Mtu Aero Engines Gmbh Paddle that has a set of ribs with an abrasive coating
FR2985759B1 (en) * 2012-01-17 2014-03-07 Snecma MOBILE AUB OF TURBOMACHINE
US20130230379A1 (en) * 2012-03-01 2013-09-05 General Electric Company Rotating turbomachine component having a tip leakage flow guide
CN102926819A (en) * 2012-10-23 2013-02-13 如皋透平叶片制造有限公司 Anti-channeling dynamic integral shroud of turbine blade
FR3001759B1 (en) 2013-02-07 2015-01-16 Snecma ROUGE AUBAGEE OF TURBOMACHINE
US10167729B2 (en) 2013-03-15 2019-01-01 United Technologies Corporation Knife edge with increased crack propagation life
FR3072121B1 (en) * 2017-10-06 2021-07-30 Safran Aircraft Engines SEALING DEVICE BETWEEN ROTOR AND TURBOMACHINE STATOR
FR3073595B1 (en) 2017-11-15 2020-02-07 Safran Helicopter Engines LABYRINTH JOINT COMPRISING A STICK WITH A DEFLECTOR
GB201801296D0 (en) * 2018-01-26 2018-03-14 Rolls Royce Plc Circumferental seal
FR3095025B1 (en) * 2019-04-12 2021-03-05 Safran Aircraft Engines Labyrinth seal comprising an abradable element with variable cell density
FR3128970A1 (en) 2021-11-05 2023-05-12 Safran Aircraft Engines LABYRINTH SEALING DEVICE FOR AN AIRCRAFT TURBOMACHINE
FR3139856B1 (en) * 2022-09-21 2024-09-06 Safran Aircraft Engines TURBOMACHINE WHEEL

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FR2615254A1 (en) * 1987-05-13 1988-11-18 Snecma MOBILE BLOWER BLADE COMPRISING AN END END
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2415003C2 (en) * 2005-11-15 2011-03-27 Снекма Method of producing rib on vane free end, vane produced by said method and gas turbine engine equipped with said vane

Also Published As

Publication number Publication date
US6939104B2 (en) 2005-09-06
FR2825411B1 (en) 2003-09-19
ES2240670T3 (en) 2005-10-16
CA2448802A1 (en) 2002-12-05
EP1262633B1 (en) 2005-03-16
WO2002097241A1 (en) 2002-12-05
FR2825411A1 (en) 2002-12-06
RU2296226C2 (en) 2007-03-27
JP2004526899A (en) 2004-09-02
DE60203214D1 (en) 2005-04-21
EP1262633A1 (en) 2002-12-04
DE60203214T2 (en) 2006-03-23
US20040146404A1 (en) 2004-07-29
CA2448802C (en) 2009-01-13
JP4074244B2 (en) 2008-04-09

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